Laser Orbital Transfer Vehicle for Space Solar Pumped Laser Power Station
- Paper number
IAC-05-C3.4-D2.8.02
- Author
Dr. Shigeaki Uchida, Tokyo Institute of Technology, Japan
- Year
2005
- Abstract
Laser power station using space solar power, SSP has been studied in terms of its feasibility under JAXA initiative. The total weight of the system is estimated to be 10,000 tons, while the construction period needs to be reasonably short (an order of a few years) to ensure its economical significance. Therefore establishing reliable and economical space transportation system is one of the most significant key factors for the system feasibility. The requirements for the transportation system are (1) high propellant usage (high specific impulse), (2) reasonably large thrust (high power handling capability), (3) reusable system with highly reliable engine, and also (4) it is desirable that the transportation system is compatible with the SSP system. We are proposing laser propulsion technology to satisfy such requirements. Laser propulsion uses high temperature plasma ablation as propellant. The velocity of the propellant can easily achieve 100 m/s, equivalent to 10,000 s specific impulse, Isp and be controlled. Large thrust is also accessible by controlling plasma temperature that is equivalent to changing laser intensity on the propellant or specific energy, Q*, defined as laser energy absorbed by unit mass of propellant. One of the advantages of laser propulsion technique is that system operating parameter can be optimized very easily, depending on the power availability and the rate of transportation. In the presentation, laser orbital transfer vehicle concept will be discussed in terms of its speculated performance based on the present laboratory experiments.
- Abstract document
- Manuscript document
IAC-05-C3.4-D2.8.02.pdf (🔒 authorized access only).
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